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Acceleration, Stress, and Deflection Measurements on the XB-15 Bomber in Gusty Air
From Introduction: "This report presents the results of these tests which cover a total of about 70 flying hours on this airplane."
Date:
June 1939
Creator:
Pearson, Henry A.
System:
The UNT Digital Library
Accelerations and bottom pressures measured on a B-24D airplane in a ditching test
From Introduction: "This report presents only that portion of the data from the first ditching which was to be used roughly establish the accelerations experienced by the pilot and the amount of water pressure to which the fuselage structure was subjected during the ditching."
Date:
November 1944
Creator:
Steiner, Margaret F.
System:
The UNT Digital Library
Accelerations Measured at Center of Gravity and Along Span of the Wing of a B-24D Airplane in Landing Impacts
Report presenting measurements of a Consolidated B-24D airplane of accelerations at various points on the wing during landing impacts. landings were made with the wheels initially stationary but free to rotate, with the brakes set before contact, and with the main wheels rotating prior to contact.
Date:
August 1944
Creator:
Westfall, John R.
System:
The UNT Digital Library
Addition of Heat to a Compressible Fluid in Motion
From Introduction: "The purpose of this report is to summarize, without extended proofs, the results of a study of a simplified model of nonadiabiatic, compressible fluid flow, both subsonic and supersonic, and to state these results in a form that will make them immediately useful in providing a theoretical background for current technical problems of high-speed combustion.
Date:
February 1945
Creator:
Hicks, Bruce L.
System:
The UNT Digital Library
Additional design charts relating to the stalling of tapered wings
From Introduction: "The present report, therefore, may be considered a supplement to reference 1. The combined scope of the stall charts of reference 1, designated A, and of the present work, designated B, is summarized in the following table: For the wing with root thickness ratio to 18 was also investigated.
Date:
January 1943
Creator:
Harmon, Sidney M.
System:
The UNT Digital Library
An Additional Investigation of the High-Speed Lateral-Control Characteristics of Spoilers
Report presenting an investigation of the characteristics of partial-span spoilers located at 0.75 of the chord on an NACA 66-series tapered wing, especially at high speeds. The effect of small spoiler projections was found to increase with an increase in speed until the critical Mach number was exceeded.
Date:
June 1945
Creator:
Laitone, Edmund V. & Summers, James L.
System:
The UNT Digital Library
Additional power-on wind-tunnel tests of the 1/8-scale model of the Brewster F2A airplane with full-span slotted flaps
"Additional tests as recommended in reference 1 were made in the 7- by 10-foot wind tunnel of the 1/8-scale model of the Brewster F2A airplane to determine the angle of attack of horizontal tail and the elevator angles required for trim with flaps down" (p. 1).
Date:
October 1941
Creator:
Lowry, John G.
System:
The UNT Digital Library
Adjustment of Stick Force by a Nonlinear Aileron-Stick Linkage
Report presenting an application of the principle of aileron-stick forces and mechanical advantage to an aileron installation in which the stick forces are small over the low-deflection range and excessively large at full deflection.
Date:
November 1942
Creator:
Lowry, John G.
System:
The UNT Digital Library
The Advantages of Uniform Fuel Distribution for Air-Cooled Engines From Considerations of Cooling Requirements and Fuel Economy
"The purpose of this report is to show by analysis of existing data, pending direct experimental determination, the extent to which nonuniform distribution of fuel to cylinders of a multicylinder engine can produce temperature deviation and the benefits to be anticipated from attainment of uniform fuel distribution" (p. 1).
Date:
December 1943
Creator:
Rubert, K. F.; Corson, Blake W., Jr. & Nielsen, Jack
System:
The UNT Digital Library
Aerodynamic and Hydrodynamic Tests of a Family of Models of Flying-Boat Hulls Derived From a Streamline Body: NACA Model 84 Series
Report presenting a series of related flying-boat hull forms with various combinations of aerodynamic and hydrodynamic requirements that were tested in an NACA tank and high-speed tunnel. Effects explored included varying the height of the bow, varying the height of the stern, increasing the angle of dead rise at the bow, decreasing the angle of dead rise on the afterbody, increasing the depth of step, increasing the angle of afterbody keel, adding chine flare, adding a third planing surface, and rounded chines at the bow.
Date:
September 1943
Creator:
Parkinson, John B.; Olson, Roland E.; Draley, Eugene C. & Luoma, Arvo A.
System:
The UNT Digital Library
Aerodynamic characteristics and flap loads of perforated double split flaps on a rectangular NACA 23012 airfoil
From Introduction: "The results of the load tests and some additional aerodynamic characteristics of perforated double split flaps on a rectangular NACA 23012 airfoil are given in the present report."
Date:
January 1943
Creator:
Turner, Thomas R.
System:
The UNT Digital Library
Aerodynamic Characteristics and Flap Loads of the Brake-Flap Installation on the 0.40-Scale Model of the F4F-3 Left Wing Panel
"The data are presented in coefficient form and include lift, drag, and pitching-moment coefficients of the airfoil-flap comoinations and the normal-force, chord-force, and hinge-moment coefficients of the upper (perforated split) flap and lower (slotted) flap" (p. 1).
Date:
October 1942
Creator:
Purser, Paul E. & Liddell, Robert B.
System:
The UNT Digital Library
Aerodynamic Characteristics for Internal-Balance and Frise Type Ailerons on an NACA 6 Series Low-Drag Tip Section of the Wing for the XP-63 Airplane
Report presenting testing in the two-dimensional turbulence tunnel of a model of the tip section of the wing of the XP-63 airplane. Several alterations of the skirts and balance on the internal-balance aileron were tested to obtain various aerodynamic characteristics of the aileron.
Date:
October 1942
Creator:
Underwood, William J.
System:
The UNT Digital Library
Aerodynamic Characteristics of a 1/8-Scale Powered Model of a High-Speed Bomber With a Dual Pusher Propeller Aft of the Empennage
Report presenting wind-tunnel tests made to determine the aerodynamic characteristics of a scale model of a high-speed bomber with a dual pusher propeller aft of the empennage. Some of the results discussed include longitudinal, lateral, and directional stability and control, the empennage design, and ground effects on the aerodynamic characteristics. The results indicate that this particular airplane has several advantages with regard to stability and control over the conventional-type single-engine airplane configuration.
Date:
October 12, 1945
Creator:
Weiberg, James A. & Schnurbusch, Alfred W.
System:
The UNT Digital Library
Aerodynamic Characteristics of a 4-Engine Monoplane Showing Comparison of Air-Cooled and Liquid-Cooled Engine Installations
From Introduction: "An investigation has been conducted in the N.A.C.A. full-scale wind tunnel to determine the aerodynamic characteristics of a 1/4-scale model of a 4-engine monoplane when equipped with comparable air-cooled engine and liquid-cooled engine installations. The air-cooled engine installation consisted of nacelles equipped with N..A.C.A. cowlings and oil coolers located in the leading edge of the wing."
Date:
July 1939
Creator:
Silverstein, Abe & Wilson, Herbert A., Jr.
System:
The UNT Digital Library
Aerodynamic Characteristics of a 4-Engine Monoplane Showing Effects of Enclosing the Engines in the Wing and Comparisons of Tractor- and Pusher-Propeller Arrangements
Report presenting testing in the full-scale wind tunnel on a model of a large 4-engine monoplane to determine the overall aerodynamic efficiency of a conventional wing-nacelle-engine installation as compared with power-plant installations enclosed in the wing with extension shafts to the propellers. Results regarding power-on and power-off performance for the installations as well as propeller noise are provided.
Date:
April 1938
Creator:
Silverstein, Abe & Wilson, Herbert A., Jr.
System:
The UNT Digital Library
Aerodynamic Characteristics of a Slot-Lip Aileron and Slotted Flap for Dive Brakes
From Introduction: "As a part of this investigation, a study is being made of test results obtained during the development of devices designed primarily for other purposes, such as high lift or lateral control, but which may also be used for dive control. These results have been reanalyzed and are herein presented in a form that should make them convenient for design purposes."
Date:
April 1941
Creator:
Rogallo, F. M.
System:
The UNT Digital Library
Aerodynamic Characteristics of Four NACA Airfoil Sections Designed for Helicopter Rotor Blades
"The purpose of the present work is to extend the previous investigation and to derive additional airfoil sections designed to minimize the undesirable characteristics of the previously tested airfoils. The tests of these additional airfoils were made in the Langley two-dimensional low-turbulence tunnel (LTT)" (p. 2).
Date:
February 1946
Creator:
Stivers, Louis S., Jr. & Rice, Fred J., Jr.
System:
The UNT Digital Library
Aerodynamic Characteristics of Several Modifications of a 0.45-Scale Model of the Vertical Tail of the Curtiss XP-62 Airplane
"In the course of an investigation to find a satisfactory vertical tail for the XP-62 airplane, a 0.45-scale vertical tail model on a stub fuselage was tested in the Langley 7- by 10-foot tunnel. This model was fitted with a flat plate to represent the horizontal tail surface. The data are presented herein for their general interest value rather than their application to this particular airplane" (p. 1).
Date:
July 1946
Creator:
Lowry, John G.; Turner, Thomas R. & Liddell, Robert B.
System:
The UNT Digital Library
Aerodynamic Characteristics of the NACA 747A315 and 747A415 Airfoils From Tests in the NACA Two-Dimensional Low-Turbulence Pressure Tunnel
Report presenting two low-drag airfoils, the NACA 747A315 and the NACA 747A415, which are designed to have reduced pitching moments about the quarter-chord point and moderately high values of the design lift coefficient and are tested in the tow-dimensional low-turbulence pressure tunnel.
Date:
September 1944
Creator:
von Doenhoff, Albert E. & Stivers, Louis S., Jr.
System:
The UNT Digital Library
Aerodynamic Data for a Wing Section of the Republic XF-12 Airplane Equipped With a Double Slotted Flap
Report presenting an investigation in the two-dimensional low-turbulence tunnels for the purpose of developing an optimum flap configuration for maximum lift on an airfoil section for the Republic XF-12 airplane equipped with a double slotted flap. Lift and flap loads were obtained at several flap deflections for two flap paths. Results regarding lift, drag, and flap loads are provided.
Date:
January 1946
Creator:
Cahill, Jones F.
System:
The UNT Digital Library
Aerodynamic Factors Affecting the Ability of a Pilot to Return an Airplane to Level From a Banked Attitude by Use of the Rudder Alone and Without Change of Heading
Report presenting a study of the aerodynamic factors upon which the ability to perform the maneuver depends in an attempt to obtain a better understanding of the conditions involved and, if possible, to evolve criterions that may be used during design.
Date:
October 1941
Creator:
Harmon, S. M.
System:
The UNT Digital Library
Aerodynamic problems in the design of efficient propellers
From General Analysis: "The purpose of part I of this paper is to show how the loading that gives the minimum induced energy loss can be obtained from rather elementary considerations and to present design charts from which such a plan form can be quickly obtained for any set of design conditions."
Date:
August 1942
Creator:
Feldman, Lewis
System:
The UNT Digital Library
Aerodynamic Tests of a Full-Scale TBF-1 Aileron Installation in the Langley 16-Foot High-Speed Tunnel
"This report describes tests in the Langley 16-foot high-speed tunnel to determine whether these failures could be attributed to changes in the aerodynamic characteristics of the ailerons at high speeds" (p. 1).
Date:
December 1944
Creator:
Becker, John V. & Korycinski, Peter F.
System:
The UNT Digital Library